Magnetic suspension bearing system for thin-walled drum blade rotor and gas turbine thereof

Abstract

The application relates to the technical field of gas turbines, in particular to a magnetic suspension supporting system of a thin-wall drum cylinder blade rotor and a gas turbine, and the magnetic suspension supporting system comprises a low-temperature end magnetic bearing system, a casing, a gas turbine rotor, a sealing structure, a high-temperature end magnetic bearing system, a temperature detection and control system and a high-temperature resistant bus; the gas turbine rotor is arranged in the casing, the low-temperature end of the gas turbine rotor is supported by the low-temperature end magnetic bearing system, and the high-temperature end is supported by the high-temperature end magnetic bearing system; the sealing structure is used for connecting the magnetic bearing system and the gas turbine rotor; the low-temperature end high-temperature resistant bus is led out from the high-temperature and low-temperature end magnetic bearing system and connected to a control terminal box in the temperature detection and control system. Compared with the prior art, the magnetic suspension supporting system designed by the application can support the thin-wall drum cylinder rotor system through the design of discrete inner and outer actuators, can weaken the influence of the high-temperature environment on the thin-wall drum cylinder rotor, and can improve the stability of the thin-wall drum cylinder rotor operation.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and in particular to a magnetic levitation support system for a thin-walled drum-bladed disk rotor and the gas turbine thereof. Background Technology

[0002] A gas turbine is a rotary power machine that uses continuously flowing gas as its working fluid and converts thermal energy into mechanical work. The hollow shaft design is a crucial structural feature for achieving high rigidity, low weight, and excellent operating performance. The thin-walled drum rotor, operating in a high-temperature environment, is a core component of the gas turbine. During operation, the ambient temperature around the rotor can reach over 1000℃, causing significant thermal deformation of the thin-walled rotor. Magnetic bearings offer advantages such as non-contact operation, wear-free operation, high speed, and high safety. Applying them to the thin-walled rotor structure of gas turbines can effectively improve their speed and service life. However, the gas turbine rotor system is subjected to high-temperature alternating thermal loads, resulting in thermoelastic coupling vibrations that often make it difficult to control the vibrations of existing magnetic bearing systems. The complex disc-blade-shaft structure of gas turbines, the design of sensor wiring arrangements, the limited range of magnetic bearing rotor control methods, and imperfect temperature compensation designs all make it difficult to apply conventional magnetic bearings to gas turbine rotors. Therefore, the design of a magnetic levitation support system under high-temperature thermal loads is particularly important.

[0003] Due to the continuous increase in the speed and efficiency of rotating machinery, the gaps between gas turbine blades and the casing and seals are gradually decreasing. Imbalance in the rotor system and shaft bending can easily cause rotor rubbing failures, leading to system instability and a series of adverse consequences. Therefore, the design of the magnetic bearing arrangement and control system components is crucial for improving the load-bearing capacity and stability of the magnetic bearings. Invention patent 202121991379.9 designs a magnetic levitation gas turbine rotor, using magnetic bearings to support the rotor and employing an integrated disc-drum structure for the compressor rotor to improve overall stability. Invention patent 202121081931.0 designs a hollow rotor structure for a gas turbine supported by magnetic bearings, using a two-stage turbine structure to circulate air for cooling the blades. Utility model 202121876726.3 designs a gas turbine using air-bearing bearings, abandoning traditional fixed supports and using air-bearing bearings to improve the lifespan and performance of the entire micro gas turbine. Invention patent 202210422896.7 proposes a nonlinear control system for a magnetic bearing with a variable operating point. Only one set of outer actuators controls the rotor, resulting in lower control accuracy compared to systems with actuators synchronously positioned on both the inner and outer sides. Utility model 202220052437.X designs an integrated structure of a magnetic levitation bearing and displacement sensors. This integrated structure has four radial displacement sensors and two axial displacement sensors arranged circumferentially in the radial direction. This design is not suitable for situations where the displacement changes throughout the entire rotation of a flexible rotor.

[0004] In the existing technology, there is insufficient disclosure of the magnetic bearing supported gas turbine rotor, magnetic bearing structure, magnetic bearing fixed support structure, and internal sensor wiring structure. The commonly used unidirectional actuator control can only generate suction in one direction, which may cause the actuator on the suction side to undergo significant thermal deformation at the same time. Under the action of suction and thermal deformation, the deformation of the thin-walled rotor becomes more obvious, which will cause rubbing. Similarly, without a temperature compensation mechanism, the single magnetic bearing control may also cause control misalignment under the influence of high temperature thermal alternation in the gas turbine. Once such a situation occurs, it will lead to rubbing failure between the blades and the casing.

[0005] In summary, there is still a lack of a magnetic levitation support system and its gas turbine for thin-walled drum-shaped bladed disk rotors operating in high-temperature environments.

[0006] The following section analyzes the principles of three common magnetic bearing models in existing technologies, and through this analysis, presents the working principle and advantages of the magnetic bearing model selected in this invention. The principles of the three magnetic bearings are analyzed as follows:

[0007] The design principle diagram of magnetic bearing model A is as follows: Figure 1As shown, the magnetic bearing model A consists of a displacement sensor and an actuator. The actuator and displacement sensor are evenly distributed along the circumference inside the thin-walled rotor. When the rotor undergoes inward deformation, the actuator moves closer to the rotor, increasing the electromagnetic attraction. The rotor system needs to reduce the electromagnetic attraction, which can only be achieved by reducing the control current of the actuator, but it is difficult to obtain an appropriate electromagnetic force. This thin-walled rotor magnetic bearing model is suitable for rigid rotors that are not easily deformable, but not for thermoelastic coupling flexible rotor systems.

[0008] The design schematic diagram of magnetic bearing model B is as follows: Figure 2 As shown, the two actuators of the magnetic bearing are differential to generate electromagnetic force, with one actuator powered by a current I. X With control current I O Driven by the sum of the currents, another actuator with a phase angle of 180° is driven by current I. X With control current I O In differential drive, the actuator can only generate attraction in one direction. When the deformation at the top of the rotor approaches the top actuator, the bottom actuator needs to generate attraction. However, if the deformation on the bottom side also approaches the bottom actuator at this time, the attraction applied to the bottom of the rotor can easily cause friction. Ignoring external loads, the vibration shape of an unconstrained thin-walled rotor under thermal loads is irregular (see the results discussion below), and the aforementioned friction can occur between the rotor and the actuator. This differential control model is applicable to undeformable rigid rotors but not to thermoelastically coupled flexible rotors.

[0009] The schematic diagram of magnetic bearing model C is as follows: Figure 3 As shown, the control unit of the magnetic bearing consists of a pair of actuators and a sensor, with multiple control units evenly distributed along the circumference of the thin-walled drum. At each location subjected to electromagnetic force, a pair of actuators is operated by differential control as described in Model B to modulate the effects of thermal deformation. This magnetic bearing model is more suitable for flexible thin-walled rotors with thermal deformation.

[0010] Figure 4 The vibration response of three magnetic bearing rotor models was simulated. Figure 4 (a) shows the displacement-current time response of the magnetic bearing actuators at the left and right ends of magnetic bearing model A. Figure 4 The upper panel diagram of (a) shows the displacement-current time response at one of the actuators of the left magnetic bearing, and the lower panel diagram shows the displacement-current time response at one of the actuators of the right magnetic bearing. It can be found that within 0.03s, the displacement at the actuator of the rotor system has exceeded the air gap (0.5mm), which will cause the blade to rub against the magnetic bearing. Figure 4(b) The thermoelastic coupling mode shape of the thin-walled rotor under unconstrained conditions can be found to be irregular along the circumferential direction at both ends of the rotor. Selecting magnetic bearing model B may cause friction between the rotor and the actuator. Figure 4 (c) shows the displacement-current time response at the magnetic bearing actuators at the left and right ends of the magnetic bearing model C. Figure 4 The upper panel plot of (c) shows the displacement-current time response of the left magnetic bearing, and the lower panel plot shows the displacement-current time response of the right magnetic bearing. It can be found that the current curve and the deformation curve at the actuator are antisymmetric, which can help the rotor stabilize at the equilibrium position. Moreover, the thermo-elastic coupling vibration response is stable and controllable. This shows that the magnetic bearing model C is suitable for thin-walled drum flexible rotor system with thermo-elastic coupling vibration. Summary of the Invention

[0011] The purpose of this invention is to provide a magnetic levitation support system for a thin-walled drum-shaped impeller rotor, based on the magnetic bearing model C in the background art, to realize the support of the thin-walled drum rotor system with thermoelastic coupling vibration.

[0012] The technical solution for achieving the objective of this invention is as follows: a magnetic levitation support system for a thin-walled drum-shaped bladed disk rotor, comprising a low-temperature end magnetic bearing system, a casing, a gas turbine rotor, a sealing structure, a high-temperature end magnetic bearing system, a temperature detection and control system, and a high-temperature resistant busbar; the gas turbine rotor is disposed inside the casing and is supported by both the low-temperature and high-temperature end magnetic bearing systems; the sealing structure is used to connect the high-temperature and low-temperature end magnetic bearing systems to the gas turbine rotor; the high-temperature and low-temperature end high-temperature resistant busbars are led out from the magnetic bearing systems and connected to the control terminal box in the temperature detection and control system; the high-temperature and low-temperature end magnetic bearing systems are equipped with execution control units for generating magnetic force to support the gas turbine rotor; the temperature detection and control system is used to detect, control, and regulate the stable operation of the gas turbine rotor; the control execution unit includes an outer ring actuator, an inner ring actuator, and a displacement sensor. A gas turbine comprising the magnetic levitation support system for a thin-walled drum-shaped bladed disk rotor as described in any one of claims 1-11.

[0013] A gas turbine, characterized in that it comprises a magnetic levitation support system for a thin-walled drum bladed disk rotor as described in any one of claims 1-11.

[0014] The significant advantages of this invention compared to existing technologies are:

[0015] 1. This solution addresses the thermoelastic coupling vibration caused by high-temperature environments by designing a magnetically levitated bearing actuator with discretely distributed actuators at both ends, applied to a thin-walled rotor. Each control unit of the magnetic bearing consists of a pair of internal and external actuators and a displacement sensor. At each location subjected to electromagnetic force, the pair of actuators generates electromagnetic force through differential control to mitigate the effects of thermal deformation. Multiple sets of control units are evenly distributed along the circumference at both ends of the thin-walled rotor. This allows deformation at any point on either end of the rotor to be detected by the control units, achieving effective control under thermoelastic coupling vibration and improving the stability of rotor operation.

[0016] 2. This solution addresses the challenges of intense thermal alternation and excessive axial temperature gradient distribution in thin-walled gas turbine rotors under high-temperature thermal loads by designing a time-varying temperature compensation scheme. Different constant exhaust temperatures alter the magnitude of the axial thermal gradient in the thin-walled rotor. Sudden increases or decreases in the gas turbine load can cause bending deformation of the rotor, leading to rubbing between the blades and the casing. This solution utilizes thermocouple sensors arranged axially at both the inlet and outlet of the casing to detect the axial temperature gradient of the thin-walled rotor. When a change in the rotor's ambient temperature is detected, the controller parameters are promptly corrected based on the signals collected by the thermocouple sensors. The discrete-distributed control actuator receives the signals and adjusts the magnitude of the electromagnetic force to suppress thermal vibration of the thin-walled rotor system, achieving temperature compensation. Furthermore, displacement sensors in the internal actuator brackets detect unique information about the thin-walled rotor. If the rotor position shifts during operation, the fault warning system reacts, and the PD parameters are adjusted again to stabilize the rotor system.

[0017] 3. This solution addresses the complex disc-plate-shaft structure of gas turbines combined with internal airflow by designing a discrete distributed multi-actuator magnetic bearing structure. Through the design of controller wiring layout, sealing rings, multi-actuator mounting and fixing structure, and guide vane disk, the installation of the complex thin-walled rotor magnetic bearing system is realized. The structure is simple and easy to install.

[0018] 4. Two types of internal actuator mounting brackets are provided to meet different requirements for thin-walled rotors. The first type: For gas turbines with short, thin-walled rotor structures and a few turbine stages, the internal actuator mounting brackets are installed at both ends. The second type: For gas turbines with long-span thin-walled rotors and a large number of turbine stages, due to the complex internal structure of the gas turbine, the inner and outer ring actuator brackets cannot be designed as a single unit. In this case, an inner ring actuator connecting bracket is designed and installed inside the multi-stage bladed disk rotor of the gas turbine. An integrated inner and outer ring actuator bracket is designed at the low-temperature end of the gas turbine rotor, and another inner ring actuator bracket is designed at the high-temperature end, with the two connected by the inner ring actuator connecting bracket. Attached Figure Description

[0019] Figure 1 Design a schematic diagram for magnetic bearing model A; where (a) is a schematic diagram of the installation structure of magnetic bearing model A, and (b) is a cross-sectional view of the internal structure of the thin-walled rotor of magnetic bearing model A.

[0020] Figure 2 Design a schematic diagram for magnetic bearing model B;

[0021] Figure 3 Design a schematic diagram for magnetic bearing model C;

[0022] Figure 4 The images show a comparison of three magnetic bearing models. (a) shows the displacement-current time response of the actuator at 90° on both ends of magnetic bearing model A; (b) shows the thermoelastic coupling vibration shape of the unconstrained thin-walled rotor of magnetic bearing model B; (c) shows the displacement-current time response of the actuator at 90° on both ends of magnetic bearing model C. (b1) is a 3D view of the thermoelastic coupling vibration shape, and (b2) is a planar projection view of the thermoelastic coupling vibration shape.

[0023] Figure 5 This is a schematic diagram of the overall structure of the magnetic levitation support system;

[0024] Figure 6 This is a cross-sectional view of the overall structure of the magnetic levitation support system;

[0025] Figure 7 This is an exploded view of the magnetic levitation support system structure.

[0026] Figure 8 Exploded view of the low-temperature magnetic bearing system;

[0027] Figure 9 This is a schematic diagram of the overall structure of the low-temperature magnetic bearing system.

[0028] Figure 10 This is a cross-sectional view of the overall structure of the low-temperature magnetic bearing system.

[0029] Figure 11 This is a partial sectional view of the internal and external actuators of the low-temperature magnetic bearing system.

[0030] Figure 12 This is a cross-sectional view of the stationary guide vane disk at the cryogenic end of a gas turbine.

[0031] Figure 13 This is a schematic diagram of the internal and external actuator support structure at the low-temperature end;

[0032] Figure 13 (a) is a schematic diagram of the structure of the inner and outer actuator brackets at the low temperature end, where (a) is a schematic diagram of the end face structure of the inner and outer actuator brackets at the low temperature end, and (b) is a cross-sectional view of the inner and outer actuator brackets at the low temperature end.

[0033] Figure 14 A schematic diagram of a stationary guide vane disk at the low-temperature end of a gas turbine;

[0034] Figure 15 This is a drawing of the inner and outer actuator brackets and actuator assembly for the low-temperature end.

[0035] Figure 16 Schematic diagram of the inner and outer actuator brackets at the low temperature end;

[0036] Figure 17 Schematic diagram of the inner and outer ring actuators of a magnetic bearing system;

[0037] Figure 18 This is an exploded view of a high-temperature magnetic bearing system.

[0038] Figure 19 This is a schematic diagram of the overall structure of the high-temperature magnetic bearing system.

[0039] Figure 20 This is a cross-sectional view of the overall structure of the high-temperature end magnetic bearing system;

[0040] Figure 21 This is a partial sectional view of the internal and external actuators of the high-temperature magnetic bearing system.

[0041] Figure 22 A schematic diagram of a stationary guide vane disk at the high-temperature end of a gas turbine;

[0042] Figure 23 This is a drawing showing the inner and outer actuator brackets and actuator assembly at the high-temperature end.

[0043] Figure 24 Schematic diagram of the inner and outer actuator brackets at the high-temperature end;

[0044] Figure 25 This is a schematic diagram of the sealing structure of a magnetic levitation support system;

[0045] Figure 26 This is a cross-sectional view of the overall structure of the magnetic levitation bearing support system for a multi-stage bladed disk rotor of a gas turbine supported by magnetic levitation bearings.

[0046] Figure 27 Exploded view of the overall structure of the magnetic levitation bearing support system for a multi-stage bladed disk rotor of a gas turbine.

[0047] Figure 28 This is an exploded view of the overall structure of the magnetic bearing system at the high-temperature end of a multi-stage bladed disk rotor in a gas turbine.

[0048] Figure 29 This is a schematic diagram of the overall structure of the high-temperature end magnetic bearing system of a multi-stage bladed disk rotor in a gas turbine.

[0049] Figure 30 A cross-sectional view of the overall structure of the magnetic bearing system at the high-temperature end of a multi-stage bladed disk rotor in a gas turbine.

[0050] Figure 31 A partial sectional view of the internal and external actuators of the high-temperature end magnetic bearing system of a multi-stage bladed disk rotor in a gas turbine.

[0051] Figure 32 Schematic diagram of a stationary guide vane at the high-temperature end of a multi-stage bladed disk rotor of a gas turbine;

[0052] Figure 33 This is a drawing showing the internal and external actuator supports and actuator assembly for the high-temperature end of a multi-stage bladed disk in a gas turbine.

[0053] Figure 34 Schematic diagram of the high-temperature outer ring actuator support for a multi-stage bladed disk in a gas turbine;

[0054] Figure 35 Schematic diagram of the high-temperature inner ring actuator support for a multi-stage bladed disk in a gas turbine.

[0055] Figure 36 This is an assembly diagram for the connection of the inner ring actuator bracket of a multi-stage bladed disk in a gas turbine.

[0056] Figure 37 Schematic diagram of the connecting bracket for the inner ring actuator of a multi-stage bladed disk rotor of a gas turbine;

[0057] Figure 38 Block diagram of the internal temperature sensor compensation control for the casing;

[0058] 1-Low-temperature end magnetic bearing system; 2-Casing; 3-Control terminal box; 4-Gas turbine rotor; 5-Sealing structure; 6-High-temperature end magnetic bearing system; 7-Thermocouple sensor; 8-High-temperature resistant busbar; 9-Low-temperature end stationary guide vane disk; 10-Low-temperature end inner and outer actuator bracket; 11-Magnetic core; 12-Outer ring actuator; 13-Inner ring actuator; 14-Displacement sensor; 15-First thickened stationary blade; 16-Low-temperature end casing guide vane disk connecting plate; 17-Low-temperature guide vane disk arc-shaped guide plate; 18-Low-temperature end high-temperature resistant busbar wiring hole; 19-Low-temperature guide vane disk and casing connection mounting hole; 20-Control actuator unit lead wire integration box; 21-Displacement sensor mounting base; 22-Low-temperature end inner and outer actuator bracket control actuator unit integration box. Wire trough; 23-Outer actuator fixing plate of low-temperature end inner and outer actuator bracket; 24-Lower-temperature end outer actuator fixing hole; 25-Lower-temperature end inner actuator fixing hole; 26-Inner actuator fixing plate of low-temperature end inner and outer actuator bracket; 27-Lower-temperature end reinforcing rib; 28-Actuator core; 29-Actuator core riveting hole; 30-Actuator coil; 31-High-temperature end inner and outer actuator bracket; 32-High-temperature end stationary guide vane; 33-High-temperature guide vane arc-shaped guide plate; 34-High-temperature end high-temperature resistant busbar wire hole; 35-High-temperature end casing guide vane connecting plate; 36-High-temperature guide vane and casing connection mounting hole; 37-Displacement sensor mounting base; 38-Inner actuator fixing plate of high-temperature end inner and outer actuator bracket; 39-Inner actuator fixing hole. ; 40-External actuator mounting hole; 41-High-temperature end inner and outer actuator bracket, external actuator fixing plate; 42-High-temperature end reinforcing rib; 43-Sealing structure and guide plate connection plate; 43-1-Sealing structure and bladed disk connection groove; 44-Multi-stage bladed disk rotor low-temperature end magnetic bearing system; 45-Gas turbine multi-stage bladed disk rotor; 46-Second sealing structure; 47-Multi-stage bladed disk rotor high-temperature resistant busbar; 48-Second terminal control box; 49-Second casing; 50-Multi-stage bladed disk rotor high-temperature end magnetic bearing system; 51-Multi-stage bladed disk rotor inner ring actuator connecting bracket; 52-Multi-stage bladed disk rotor thermocouple sensor; 53-Multi-stage bladed disk high-temperature inner ring actuator bracket; 54-Multi-stage bladed disk high-temperature outer ring actuator bracket; 55-Multi-stage bladed disk high-temperature... 56-High-temperature guide vane disk hollow thin plate structure; 57-Multi-stage vane disk rotor casing guide vane disk connecting plate; 58-Multi-stage vane disk rotor high-temperature guide vane disk and casing connection mounting hole; 59-Multi-stage vane disk rotor high-temperature guide vane disk arc-shaped guide plate; 60-High-temperature outer ring actuator bracket actuator fixing plate; 61-High-temperature outer ring fixed bracket actuator mounting hole; 62-Multi-stage vane disk rotor reinforcing rib; 63-Inner ring actuator fixed bracket mounting hole; 64-High-temperature inner ring actuator bracket actuator fixing plate; 65-High-temperature inner ring actuator bracket actuator mounting hole; 66-Multi-stage vane disk rotor control actuator unit lead wire integration box; 67-High-temperature inner ring fixed bracket control actuator unit cable tray; 68-High-temperature inner ring fixed bracket displacement sensor mounting base;69 - Low-temperature inner ring fixing bracket connecting rod; 70 - High-temperature inner ring fixing bracket connecting rod. Detailed Implementation

[0059] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0060] Example 1

[0061] like Figure 5-7 As shown, the present invention discloses a magnetic levitation support system for a thin-walled drum-shaped bladed disk rotor, comprising a low-temperature end magnetic bearing system 1, a casing 2, a gas turbine rotor 4, a sealing structure 5, a high-temperature end magnetic bearing system 6, a temperature detection and control system, and a high-temperature resistant busbar 8. Figure 6 As shown, the gas turbine rotor 4 (thin-walled drum rotor) is housed inside the casing 2. The gas turbine rotor 4 is supported at both ends by two magnetic bearing systems: its low-temperature end is supported by low-temperature magnetic bearing system 1, and its high-temperature end is supported by high-temperature magnetic bearing system 6. The low-temperature magnetic bearing system 1 and the gas turbine rotor 4 are connected by a sealing structure 5. The sealing structure of the high-temperature magnetic bearing system 6 is designed to be integrated with the high-temperature end stationary guide vane and connected to the gas turbine rotor 4. One end of the low-temperature end high-temperature resistant busbar 8 is led out from the low-temperature end magnetic bearing system 1, and the other end is connected to the control terminal box 3 in the temperature detection and control system. Similarly, one end of the high-temperature end high-temperature resistant busbar 8 is led out from the high-temperature end magnetic bearing system 6, and the other end is connected to the control terminal box 3 in the temperature detection and control system. The temperature detection and control system is installed on the casing and is used to detect the internal temperature of the gas turbine and control the magnetic levitation bearings to achieve stable operation of the gas turbine rotor.

[0062] like Figure 8 As shown, the low-temperature end magnetic bearing system 1 includes a low-temperature end stationary guide vane disk 9, a low-temperature end inner and outer actuator bracket 10, a magnetic core 11, an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14. Combined with... Figure 5 The outer ring of the low-temperature stationary guide vane 9 is riveted to the inner wall of the casing 2, such as... Figure 9 and Figure 10 As shown, the inner ring of the low-temperature end stationary guide vane disk 9 is fixedly connected to the outer ring of the low-temperature end inner and outer actuator bracket 10; as Figure 11 As shown, the magnetic core 11 is made of soft magnetic ferrite material, which has good magnetoelectric properties. The outer ring of the magnetic core 11 is concentrically mounted with the inner ring of the low-temperature actuator bracket 10. The inner ring of the magnetic core 11 is interference-fitted with the low-temperature end of the gas turbine rotor 4. Therefore, the inner and outer actuators generate magnetic field force to support the magnetic core 11, and thus support the gas turbine rotor 4.

[0063] like Figure 8 and Figure 10 As shown, a set of control execution units includes an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14; as Figure 15 As shown, multiple sets of control execution units are uniformly arranged and fixedly installed in the inner and outer actuator brackets 10 at the low-temperature end along the circumference. The magnetic field force generated by the differential control of the inner and outer actuators is used to support the rotation of the gas turbine rotor 4, and the displacement sensor 14 is used to detect the displacement of the gas turbine rotor 4. In this embodiment, 15 sets of control execution units are used at the low-temperature end. The number of inner and outer ring actuators in this invention is the same, and differential control of the inner and outer ring bidirectional actuators is adopted. Therefore, the number of control execution units can be increased individually according to the control accuracy and actual structure, such as 16 sets, 17 sets, or 18 sets.

[0064] like Figure 12 and Figure 14 As shown, the gas turbine's low-temperature end stationary guide vane 9 includes a first thickened blade 15, a low-temperature end casing guide vane connecting plate 16, a low-temperature guide vane arc-shaped guide plate 17, a low-temperature end high-temperature resistant busbar through-hole 18, and a low-temperature guide vane and casing connection mounting hole 19. Figure 14 As shown, the casing guide plate 16 has eight circumferentially distributed low-temperature guide vane mounting holes 19 for connecting the casing 2 to the casing, used for fixing the casing 2 together with rivets. Figure 12 As shown, ordinary blades, a first thickened blade 15, and a second thickened blade are evenly arranged within the connecting plate 16 of the cryogenic end casing guide vane. The first thickened blade 15 and the second thickened blade are axially symmetrically installed, with the same blade thickness, to maintain the structural balance of the guide vane disk. An arc-shaped guide plate 17 of the cryogenic guide vane disk is fixed to the inner ring of the blades. The arc-shaped guide plate 17 has an arc-shaped surface, which reduces airflow resistance and evenly disperses the airflow inside the casing 2. The structural design of the cryogenic end stationary guide vane disk 9 avoids the problem of obstructing the airflow inside the gas turbine due to the installation of internal and external actuator supports. Figure 12 As shown, a low-temperature end high-temperature resistant busbar through hole 18 is opened from the low-temperature end casing guide plate 16 to the first thickened blade 15.

[0065] like Figure 16 As shown, and in combination Figure 13The low-temperature end inner and outer actuator bracket 10 includes a control actuator lead wire integration box 20, a low-temperature end displacement sensor mounting base 21, a control actuator hub 22, an outer actuator fixing plate 23, an outer actuator fixing hole 24, an inner actuator fixing hole 25, an inner actuator fixing plate 26, and a low-temperature end reinforcing rib 27. Fifteen sets of low-temperature end actuator fixing plates 23 and 26 are evenly distributed along the circumference of the low-temperature end actuator bracket 10. Each set of low-temperature end actuator fixing plates 23 has two low-temperature end actuator fixing holes 24 for fixing the outer ring actuator 12 with rivets. Similarly, each set of low-temperature end actuator fixing plates 26 has two inner ring actuator fixing holes 25 for fixing the inner ring actuator 13 with rivets. Fifteen low-temperature end displacement sensor mounting seats 21 are evenly distributed along the circumference of the inner ring of the low-temperature end actuator bracket 10 for mounting displacement sensors 14. Fifteen low-temperature end reinforcing ribs 27 are evenly distributed along the circumference of the outer ring of the low-temperature end actuator bracket 10 to enhance the strength and rigidity of the guide vane, thereby saving material, reducing weight, and lowering costs.

[0066] like Figure 13 As shown, the integrated box 20 for the control execution unit of the low-temperature end inner and outer actuator bracket is located radially on the outer side of the low-temperature end inner and outer actuator bracket, and the control execution unit cable tray 22 is located on the outer side of the low-temperature end inner and outer actuator bracket in a ring shape, with the center of the ring concentric with the outer side.

[0067] like Figures 11-13 As shown, the control execution unit lead wire of the low-temperature end magnetic bearing system is led out from the control execution unit, passes through the displacement sensor mounting base 21 or the inner and outer actuator fixing plate, extends to the control execution unit cable tray 22 of the low-temperature end inner and outer actuator bracket, and is gathered in the control execution unit lead wire integration box 20, forming a high-temperature resistant busbar 8 that passes through the low-temperature end high-temperature resistant busbar through hole 18, and then leads out of the casing 2 wall to connect to the terminal control box 3.

[0068] like Figure 17 As shown, the inner and outer ring actuators of the magnetic bearing system have the same structure. Each actuator includes an actuator core 28 and an actuator coil 30. The actuator core 28 is made of silicon steel material such as aluminum iron boron and is in the shape of an I-beam. The actuator coil 30 is wound on the actuator core 28. The actuator coil 30 is arranged in 12 turns along the longitudinal direction of the I-beam actuator core 28 and is used to generate electromagnetic force by passing electricity. The actuator core 28 has an actuator core riveting hole 29.

[0069] Figure 18As shown, the high-temperature end magnetic bearing system 6 includes a high-temperature end stationary guide vane disk 32, a high-temperature end inner and outer actuator bracket 31, a magnetic core 11, an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14. The outer ring of the high-temperature end stationary guide vane disk 32 is riveted to the inner wall of the casing 2, as shown. Figure 19 and Figure 20 As shown, the inner ring of the high-temperature end stationary guide vane disk 32 is fixedly connected to the outer ring of the high-temperature end inner and outer actuator bracket 31; the outer ring of the magnetic core 11 is concentrically rotated with the inner ring of the high-temperature end inner and outer actuator bracket 31, and the inner ring of the magnetic core 11 is interference-fitted with the high-temperature end of the gas turbine rotor 4. The installation method and function are the same as those of the magnetic core 11 in the low-temperature end magnetic bearing system 1.

[0070] like Figures 18-20 As shown, the control execution unit at the high-temperature end has the same design principle and structural composition as the control execution unit at the low-temperature end. The outer ring actuator 12, the inner ring actuator 13, and the displacement sensor 14 are fixedly installed in the inner and outer actuator brackets 31 at the high-temperature end. One control execution unit includes one outer ring actuator 12, one inner ring actuator 13, and one displacement sensor 14. Multiple sets of control execution units are evenly distributed circumferentially in the inner and outer actuator brackets 31 at the high-temperature end. The magnetic force generated by the inner and outer actuators supports the thin-walled drum rotor. The displacement sensor 14 is used to detect the displacement of the gas turbine rotor 4. In this embodiment, 15 sets of control execution units are used at the high-temperature end. The number of inner and outer ring actuators is the same in this invention, and differential control of the inner and outer ring bidirectional actuators is adopted. Therefore, the number of control execution units can be increased individually according to the control accuracy and actual structure, such as 16, 17, or 18 sets.

[0071] like Figure 22 As shown, the high-temperature end stationary guide vane 32 includes a first thickened blade 15, a high-temperature guide vane arc-shaped guide plate 33, a high-temperature end high-temperature resistant busbar through-hole 34, a high-temperature end casing guide vane connecting plate 35, and a high-temperature guide vane and casing connection mounting hole 36. Combined with... Figure 12 , Figure 21 , Figure 22 The structural difference between the high-temperature guide vane arc-shaped guide plate 33 and the low-temperature guide vane arc-shaped guide plate 17 is as follows: Figure 21 As shown, the high-temperature guide vane disk arc-shaped guide plate 33 is a hollow cavity with an inner and outer double-layer structure. The inner thin plate of the high-temperature guide vane disk arc-shaped guide plate 33 is fixedly connected to the inner and outer actuator brackets 31 at the high-temperature end, and its outer thin plate is coated with a heat-insulating coating to prevent heat conduction of the high-temperature airflow inside the casing. Figure 22As shown, the outer ring of the high-temperature end casing guide plate 35 has eight high-temperature guide vanes evenly distributed circumferentially. These vanes are fixed to the casing 2 via casing connection mounting holes 36 and rivets. The remaining structures within the high-temperature end stationary guide vane 32 (such as the first thickened blade 15, the high-temperature end high-temperature resistant busbar wiring hole 34, and the control execution unit lead wire integration box 20) are the same as the internal structure of the low-temperature end stationary guide vane 9.

[0072] like Figure 23 As shown, the high-temperature end inner and outer actuator bracket 31 includes a high-temperature end control actuator lead wire integration box, a high-temperature end displacement sensor mounting base 37, a high-temperature end inner and outer actuator bracket displacement sensor wiring channel, a high-temperature end inner actuator fixing plate 38, a high-temperature end inner actuator fixing mounting hole 39, a high-temperature end outer actuator fixing mounting hole 40, a high-temperature end outer actuator fixing plate 41, and a high-temperature end reinforcing rib 42. Figure 24 As shown, 15 sets of high-temperature end outer actuator fixing plates 41 and high-temperature end inner actuator fixing plates 38 are evenly distributed along the circumference. Each set of high-temperature end outer actuator fixing plates 41 has two high-temperature end outer actuator fixing holes 40, which are used to fix the outer actuator 12 to the outer ring via rivets. Similarly, each set of high-temperature end inner actuator fixing plates 38 has two high-temperature end inner actuator fixing holes 39, which are used to fix the inner actuator 13 to the inner ring via rivets. Fifteen high-temperature end displacement sensor mounting seats 37 are evenly distributed along the circumference of the inner ring of the high-temperature end inner and outer actuator brackets; fifteen high-temperature end reinforcing ribs 42 are evenly distributed along the circumference of the outer ring of the high-temperature end inner and outer actuator brackets to enhance the strength and rigidity of the guide vane, thereby saving material, reducing weight, and lowering costs. The position and function of the high-temperature end control actuator unit lead wire integration box and the high-temperature end inner and outer actuator bracket displacement sensor wiring groove are the same as those of the low-temperature end.

[0073] The control execution unit lead wire of the high-temperature end magnetic bearing system is led out from the control execution unit, passes through the high-temperature end displacement sensor mounting base 37 or the high-temperature end inner and outer actuator fixing plate, extends to the control execution unit cable tray of the high-temperature end inner and outer actuator bracket, and is gathered in the high-temperature end control execution unit lead wire integration box, forming a high-temperature resistant bus 8 that passes through the high-temperature end high-temperature resistant bus wire hole 34, and then leads out of the casing 2 wall and connects to the terminal control box 3.

[0074] The gas turbine sealing structure 5 adopts a graphite sealing structure, which is resistant to high temperatures and corrosion. For example... Figure 25 As shown, the sealing structure 5 includes two parts: the sealing structure and the guide plate 43 and the sealing structure and the blade disk connecting groove 43-1. The sealing structure and the guide plate 43 are connected to the low-temperature end stationary guide blade disk 9 as one unit, and the sealing structure and the blade disk connecting groove 43-1 are connected to the gas turbine rotor blade disk 4 as one unit to prevent gas from flowing into the rotor.

[0075] The temperature detection and control system includes a control terminal box 3, thermocouple sensors 7, and a fault early warning system. The control terminal box 3 houses a PD controller for data processing and control of the distributed actuators throughout the magnetic levitation support system. The fault early warning system connects the displacement sensor and the PD controller to provide warnings and responses when the rotor position deviates. Two thermocouple sensors are axially arranged at the air inlet and exhaust outlet of the casing wall, connected to the control terminal box 3 via thermocouple sensor connection lines. These sensors detect the axial temperature gradient of the thin-walled rotor. When a change in the rotor's ambient temperature is detected, the temperature signal collected by the thermocouple sensors is transmitted to the controller, which then promptly corrects the controller parameters. The discrete distributed actuators receive the controller's signal and adjust the magnitude of the electromagnetic force to suppress thermal vibration of the thin-walled rotor system, achieving temperature compensation control of the system.

[0076] The present invention discloses a control system for a magnetic levitation support system of a thin-walled drum-shaped impeller rotor, as follows: Figure 38 As shown, the working principle of the control system is as follows: Thermocouple sensor 7 detects the temperature of the rotor in the combustion chamber and transmits the collected information to the PD controller. Based on the collected signal, the PD parameters are adaptively adjusted. The adjustment of the PD parameters is converted into a change in current input to regulate the distributed internal and external actuators. By changing the magnitude of the electromagnetic force, stable control of the thin-walled gas turbine rotor system is achieved. At the same time, displacement sensor 14 monitors the displacement information of the gas turbine rotor (thin-walled drum rotor) in real time and compares it with the reference position in real time, feeding back to the PD controller. If the rotor position deviates during operation, the fault warning system will react, and at this time, the PD parameters will be adjusted again to stabilize the rotor system.

[0077] The working process between the magnetic levitation support and the temperature detection and control system of the thin-walled drum bladed disk rotor of the present invention is as follows: When the gas turbine rotor 4 rotates at high speed, the high and low temperature magnetic bearing systems installed on both sides of the gas turbine rotor 4 play a protective support role. During operation, when the rubbing clearance tends to disappear, the magnetic bearing systems at both ends detect the displacement at both ends of the rotor through the displacement sensor 14 inside the rotor system. When the displacement is too large or too small, the PD parameters of the magnetic bearing system are adjusted to stabilize the levitation control of the rotor operation. When temperature fluctuations occur inside the gas turbine, the temperature signal detected by the thermocouple sensor 7 is used. When the temperature is too high or too low, the PD parameters of the magnetic bearing system are adjusted to achieve stable control of the gas turbine rotor 4 system.

[0078] In this embodiment, the low-temperature magnetic bearing system 1 and the high-temperature magnetic bearing system 6 are located at both ends of the gas turbine rotor 4, and the bladed disk of the gas turbine rotor 4 is located in the middle.

[0079] Example 2

[0080] Example 2 describes a magnetic levitation bearing support system for a multi-stage bladed disk rotor of a gas turbine. One end of the multi-stage bladed disk rotor 45 is supported by a low-temperature magnetic bearing system 44, while the other end has a high-temperature magnetic bearing system 50 positioned in the middle of the multi-stage turbine bladed disk. This type of rotor typically has multiple turbine bladed disks. The following magnetic levitation support system is designed for this type of turbine bladed disk rotor, with the specific structure as follows:

[0081] like Figure 26 and Figure 27 As shown, the multi-stage bladed disk rotor magnetic levitation bearing support system for a gas turbine includes a multi-stage bladed disk rotor low-temperature end magnetic bearing system 44, a second casing 49, a multi-stage bladed disk rotor 45, a second sealing structure 46, a multi-stage bladed disk rotor high-temperature end magnetic bearing system 50, a temperature detection and control system, a multi-stage bladed disk rotor high-temperature resistant busbar 47, and a multi-stage bladed disk rotor inner ring actuator connecting bracket 51. The difference between the multi-stage bladed disk rotor magnetic levitation bearing support system and that in Embodiment 1 is that the multi-stage bladed disk rotor low-temperature end magnetic bearing system 44 is fixedly installed at the low-temperature end of the multi-stage bladed disk rotor 45, while the multi-stage bladed disk rotor high-temperature end magnetic bearing system 50 is placed at the turbine bladed disk in the middle position; as shown... Figure 26 As shown, the gas turbine multi-stage bladed disk rotor 45 is a hollow thin-walled drum structure. The low-temperature magnetic bearing system 44 of the multi-stage bladed disk rotor is fixedly installed at the low-temperature end of the second casing 49. The gas turbine multi-stage bladed disk rotor 45 is installed inside the second casing 49, and the high-temperature magnetic bearing system 50 of the multi-stage bladed disk rotor is fixedly installed at the high-temperature end of the second casing 49. The multi-stage bladed disk rotor inner ring actuator connecting bracket 51 is installed inside the gas turbine multi-stage bladed disk rotor 45, with its low-temperature end fixedly connected to the multi-stage bladed disk rotor low-temperature magnetic bearing system 44, and its high-temperature end fixedly connected to the multi-stage bladed disk rotor high-temperature magnetic bearing system 50. Figure 26-27 As shown, the second casing 49, temperature detection and control system, and high-temperature resistant busbar 47 of the multi-stage bladed disk rotor magnetic levitation bearing support system are the same as those in Embodiment 1; the multi-stage bladed disk rotor low-temperature end magnetic bearing system 44 and the multi-stage bladed disk rotor gas turbine rotor 45 are sealed by the second sealing structure 46; the second sealing structure 46 has the same structure as the sealing structure 5.

[0082] The technical solution of the low-temperature end magnetic bearing system 44 of the multi-stage bladed disk rotor is the same as that of the low-temperature end magnetic bearing system 1 in Example 1.

[0083] Figures 28-30 As shown, the high-temperature end magnetic bearing system 50 of the multi-stage bladed disk of a gas turbine includes a high-temperature guide vane 55, a high-temperature outer ring actuator bracket 54, a high-temperature inner ring actuator bracket 53, a magnetic core 11, an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14. Figure 29 and Figure 30 As shown, the inner ring of the high-temperature guide vane 55 of the multi-stage impeller is fixedly connected to the outer ring of the high-temperature outer ring actuator bracket 54 of the multi-stage impeller, and the high-temperature inner ring actuator bracket 53 of the multi-stage impeller is concentrically (rotatably) connected to the high-temperature outer ring actuator bracket 54 of the multi-stage impeller; combined with Figure 31 The outer ring actuator 12 is installed in the high-temperature outer ring actuator bracket 54 of the multi-stage bladed disk, while the inner ring actuator 13 and displacement sensor 14 are fixedly installed in the high-temperature inner ring actuator bracket 53 of the multi-stage bladed disk. The outer ring of the magnetic core 11 is concentrically rotated with the inner ring of the actuator bracket 53 within the high-temperature inner ring actuator bracket of the multi-stage bladed disk; the inner ring of the magnetic core is fixedly connected to the multi-stage bladed disk rotor 45 of the gas turbine.

[0084] like Figure 33 and Figure 34 As shown, a control execution unit includes an outer ring actuator 12, an inner ring actuator 13, and a displacement sensor 14. Multiple sets of control execution units are evenly distributed circumferentially on the high-temperature end support 53 of the multi-stage impeller. The magnetic force generated by the inner and outer actuators supports the thin-walled drum rotor. The displacement sensor 14 is used to detect rotor displacement. This invention employs differential control of inner and outer ring bidirectional actuators. The number of inner and outer ring actuators is the same. This embodiment uses 15 sets of control execution units. The number of actuator units can be increased individually according to the control accuracy and actual structure, such as 16, 17, or 18 sets.

[0085] like Figure 31 and Figure 32 As shown, due to the influence of the high-temperature environment, the structure of the high-temperature end guide vane 55 of the gas turbine multi-stage bladed disk rotor differs from the structure of the high-temperature end stationary guide vane 32 in Embodiment 1 as follows: The hollow thin plate structure 56 of the high-temperature guide vane is a double-layer structure, with the inner thin plate fixedly connected to the outer actuator bracket 54 of the high-temperature end of the multi-stage bladed disk. The outer thin plate is coated with a heat-insulating layer to prevent heat conduction inside the second casing 49. Furthermore, the arc-shaped guide plates 59 of the high-temperature guide vane of the multi-stage bladed disk rotor are arranged on both sides of the guide vane connecting plate 57 of the multi-stage bladed disk casing, connecting the bladed disk rotors on both sides respectively. The remaining structure of the high-temperature end guide vane 55 of the multi-stage bladed disk rotor is the same as that of the high-temperature end stationary guide vane 32 in Embodiment 1.

[0086] like Figure 34 As shown, the multi-stage impeller high-temperature outer ring actuator bracket 54 includes a high-temperature outer ring actuator bracket actuator fixing plate 60, high-temperature outer ring fixed bracket actuator mounting holes 61, and multi-stage impeller rotor reinforcing ribs 62. Fifteen sets of outer actuator fixing plates 60 are evenly distributed along the circumference. Each set of high-temperature outer ring actuator bracket actuator fixing plates 60 has two high-temperature outer ring fixed bracket actuator mounting holes 61, which are used to fix the outer ring actuator 12 together with rivets. The multi-stage impeller rotor reinforcing ribs 62 are used to enhance the strength and rigidity of the guide vane, thereby saving material, reducing weight, and lowering costs.

[0087] like Figure 35 As shown, the multi-stage impeller high-temperature outer ring actuator bracket 53 includes inner ring actuator fixing bracket mounting holes 63, high-temperature inner ring actuator bracket actuator fixing plate 64, high-temperature inner ring actuator bracket actuator mounting holes 65, multi-stage impeller rotor control actuator unit lead wire integration box 66, high-temperature inner ring fixing bracket control actuator unit cable tray 67, and high-temperature inner ring fixing bracket displacement sensor mounting base 68. Four inner ring actuator fixing bracket mounting holes 63 are evenly distributed along the inner ring of the actuator bracket. Fifteen sets of high-temperature inner ring actuator bracket actuator fixing plates 64 are evenly distributed along the circumference. Each set of high-temperature inner ring actuator bracket actuator fixing plates 64 has two high-temperature inner ring actuator bracket actuator mounting holes 65, which are used to fix the inner ring actuator 13 together with rivets. Fifteen high-temperature inner ring actuator bracket displacement sensor mounting bases 68 are evenly distributed along the circumference of the inner ring of the high-temperature inner actuator bracket for mounting displacement sensors 14. The outer end face of the high-temperature inner ring actuator bracket 53 of the multi-stage bladed disk of the gas turbine is also designed with a control execution unit cable tray 67 and a control execution unit lead wire integration box 66. The lead wires of the control execution unit are collected and concentrated inside the control execution unit lead wire integration box 66 through the control execution unit cable tray 67, and then pass out through the high-temperature resistant busbar hole of the multi-stage bladed disk rotor. The specific wiring is the same as the wiring of the control execution unit in Embodiment 1.

[0088] The assembly diagram of the inner ring actuator bracket connection for the multi-stage bladed disk at both high and low temperatures of the gas turbine is shown below. Figure 36 As shown, the multi-stage impeller rotor inner ring actuator connecting bracket 51 is fixedly connected at both ends to the multi-stage impeller rotor low-temperature end magnetic bearing system 44 and the multi-stage impeller high-temperature inner ring actuator bracket 53; as Figure 37 As shown, the gas turbine multi-stage bladed disk rotor inner ring actuator connecting bracket 51 includes an intermediate connecting rod, a low-temperature inner ring fixing bracket connecting rod 69, and a high-temperature inner ring fixing bracket connecting rod 70. There are four low-temperature inner ring fixing bracket connecting rods 69, which are evenly fixed at 90° on the low-temperature end of the intermediate connecting rod. There are four high-temperature inner ring fixing bracket connecting rods 70, which are evenly fixed at 90° on the high-temperature end of the intermediate connecting rod.

[0089] The present invention also provides a gas turbine including the aforementioned magnetic levitation support system. In this embodiment, the magnetic levitation support system is disposed within the gas turbine to support the thin-walled drum rotor system subjected to thermoelastic coupling vibration, thereby reducing the influence of the high-temperature environment on the thin-walled drum rotor and improving the operational stability of the thin-walled drum rotor.

Claims

1. A magnetic levitation support system for a thin-walled drum-shaped impeller rotor, characterized in that, The magnetic levitation support system includes a low-temperature end magnetic bearing system, a casing, a gas turbine rotor, a sealing device, a high-temperature end magnetic bearing system, a temperature detection and control system, and a high-temperature resistant busbar; The gas turbine rotor is a thin-walled drum bladed disk rotor and is located inside the casing. The low-temperature end of the gas turbine rotor is supported by a low-temperature end magnetic bearing system, and the high-temperature end is supported by a high-temperature end magnetic bearing system. The sealing device includes: a sealing structure and a guide vane connecting plate that are integrated with the low-temperature end stationary guide vane disk, and a sealing structure and a vane disk connecting groove that are integrated with the gas turbine rotor vane disk, used to achieve sealing between the high-temperature end magnetic bearing system, the low-temperature end magnetic bearing system and the gas turbine rotor. The high-temperature end magnetic bearing system and the low-temperature end magnetic bearing system are equipped with circumferentially discrete and uniformly distributed control execution units to generate magnetic force to support the gas turbine rotor. Each control execution unit includes an inner and outer ring bidirectional actuator and a displacement sensor. The inner and outer ring bidirectional actuators are differentially controlled to generate electromagnetic force to weaken the effect of thermal deformation. The deformation at both ends of the gas turbine rotor is detected by the control execution unit, realizing effective control under thermo-elastic coupling vibration and improving the stability of rotor operation. Both the low-temperature end magnetic bearing system and the high-temperature end magnetic bearing system include a stationary guide vane disk, inner and outer actuator supports, a magnetic core, and a control actuator unit; the outer ring of the stationary guide vane disk is fixed to the inner wall of the casing, and the inner ring is fixedly connected to the outer ring of the inner and outer actuator supports; the outer ring of the magnetic core is concentrically rotated with the inner ring of the inner and outer actuator supports; the inner ring of the magnetic core is fixedly connected to the gas turbine rotor, and the control actuator unit is fixedly installed inside the inner and outer actuator supports; The high-temperature resistant busbars at both high and low temperatures are led out from the magnetic bearing system and connected to the control terminal box in the temperature detection and control system. Temperature detection and control system, used to detect, control and regulate the stable operation of gas turbine rotor.

2. The magnetic levitation support system for the thin-walled drum-shaped impeller rotor as described in claim 1, characterized in that, The gas turbine rotor is a multi-stage bladed disk rotor, and the high-temperature end magnetic bearing system is a high-temperature end magnetic bearing system of the multi-stage bladed disk rotor. The low-temperature end of the multi-stage bladed disk rotor is supported by the low-temperature end magnetic bearing system, and the high-temperature end magnetic bearing system of the multi-stage bladed disk rotor is located in the middle of the gas turbine rotor, thereby supporting the gas turbine rotor.

3. The magnetic levitation support system for the thin-walled drum-shaped impeller rotor as described in claim 2, characterized in that, The magnetic levitation support system also includes a multi-stage bladed disk rotor inner ring actuator connecting bracket. The gas turbine rotor is a hollow thin-walled drum structure. The multi-stage bladed disk rotor inner ring actuator connecting bracket is installed inside the gas turbine rotor. The low-temperature end of the multi-stage bladed disk rotor inner ring actuator connecting bracket is fixedly connected to the low-temperature end magnetic bearing system, and the high-temperature end is fixedly connected to the high-temperature end magnetic bearing system of the multi-stage bladed disk rotor.

4. The magnetic levitation support system for the thin-walled drum-shaped impeller rotor as described in claim 1, characterized in that, The stationary guide vane in the low-temperature magnetic bearing system is a low-temperature stationary guide vane, and the stationary guide vane in the high-temperature magnetic bearing system is a high-temperature stationary guide vane. Both include a first thickened blade, a casing guide vane connecting plate, a guide vane arc-shaped guide plate, and a high-temperature resistant busbar through hole. The casing guide vane connecting plate is fixedly connected to the casing. The first thickened blade is set inside the casing guide vane connecting plate. The inner ring of the blade is fixed with the guide vane arc-shaped guide plate. A high-temperature resistant busbar through hole is opened from the casing guide vane connecting plate to the first thickened blade. Furthermore, the high-temperature end stationary guide vane has a double-layer structure with a hollow cavity; the inner ring thin plate is fixedly connected to the inner and outer actuator brackets, and the outer ring thin plate is provided with a heat insulation coating to prevent heat conduction of the high-temperature airflow inside the casing.

5. The magnetic levitation support system for the thin-walled drum-shaped impeller rotor as described in claim 1, characterized in that, The inner and outer actuator brackets include displacement sensor mounting bases, an outer actuator fixing plate, an inner actuator fixing plate, a control actuator unit lead wire integration box, a control actuator unit wiring channel, an outer actuator fixing mounting hole, an inner actuator fixing mounting hole, and reinforcing ribs. The outer and inner actuator fixing plates are evenly distributed along the circumference of the inner and outer actuator brackets. Displacement sensor mounting bases are evenly distributed along the circumference of the inner and outer actuator brackets for mounting displacement sensors. The actuator unit lead wire integration box is located radially on the outer side of the inner and outer actuator brackets. The outer actuator fixing mounting hole is located on the outer actuator fixing plate for mounting the outer actuator. The inner actuator fixing mounting hole is located on the inner actuator fixing plate for mounting the inner actuator. Reinforcing ribs are evenly distributed along the circumference of the outer ring of the inner and outer actuator brackets to enhance the strength and rigidity of the guide vane. The control actuator unit wiring channel is located at the low-temperature end and is annular on the outer side of the inner and outer actuator brackets, with the center of the annulus concentric with the outer side.

6. The magnetic levitation support system for the thin-walled drum-shaped impeller rotor as described in claim 5, characterized in that, The control actuator leads are led out from the control actuator, pass through the displacement sensor mounting base, extend to the control actuator hub groove of the inner and outer actuator bracket, and are gathered in the control actuator lead integration box, forming a high-temperature resistant busbar that passes through the high-temperature resistant busbar through hole, and then leads out of the casing wall to connect to the terminal control box.

7. The magnetic levitation support system for the thin-walled drum-shaped impeller rotor as described in claim 3, characterized in that, The high-temperature end magnetic bearing system of the multi-stage bladed disk rotor includes a high-temperature guide vane, a high-temperature outer ring actuator bracket, a high-temperature inner ring actuator bracket, a magnetic core, and a control actuator unit. The inner ring of the high-temperature guide vane is fixedly connected to the outer ring of the high-temperature outer ring actuator bracket, and the high-temperature inner ring actuator bracket is concentrically rotatably connected to the high-temperature outer ring actuator bracket. The outer ring actuator in the control actuator unit is installed in the high-temperature outer ring actuator bracket, and the inner ring actuator and displacement sensor in the control actuator unit are fixedly installed in the high-temperature inner ring actuator bracket. The outer ring of the magnetic core is concentrically rotatably installed with the inner ring of the actuator bracket in the high-temperature inner ring actuator bracket. The inner ring of the magnetic core is fixedly connected to the gas turbine rotor.

8. The magnetic levitation support system for the thin-walled drum-shaped impeller rotor as described in claim 7, characterized in that, The multi-stage impeller high-temperature guide vane includes a first thickened blade, a hollow thin-plate structure of the high-temperature guide vane, a multi-stage impeller casing guide vane connecting plate, a multi-stage impeller high-temperature guide vane arc-shaped guide plate, and a high-temperature resistant busbar through hole. The hollow thin-plate structure of the high-temperature guide vane is a double-layer structure, with the inner thin plate fixedly connected to the external actuator bracket at the high-temperature end of the multi-stage impeller, and the outer thin plate having an added heat-insulating coating. The multi-stage impeller casing guide vane connecting plate is fixedly connected to the casing. The first thickened blade is set inside the multi-stage impeller casing guide vane connecting plate, and the inner ring of the blade is fixed with the multi-stage impeller high-temperature guide vane arc-shaped guide plate. The multi-stage impeller high-temperature guide vane arc-shaped guide plate is arranged on both sides of the multi-stage impeller casing guide vane connecting plate. A high-temperature resistant busbar through hole is opened from the multi-stage impeller casing guide vane connecting plate to the first thickened blade.

9. The magnetic levitation support system for a thin-walled drum-shaped impeller rotor as described in claim 8, characterized in that, The multi-stage bladed disk rotor inner ring actuator connecting bracket is fixedly connected at both ends to the low-temperature magnetic bearing system of the multi-stage bladed disk rotor and the high-temperature inner ring actuator bracket of the multi-stage bladed disk rotor, respectively. The gas turbine multi-stage bladed disk rotor inner ring actuator connecting bracket includes an intermediate connecting rod, a low-temperature inner ring fixing bracket connecting rod, and a high-temperature inner ring fixing bracket connecting rod. There are four low-temperature inner ring fixing bracket connecting rods, which are evenly fixed at 90° on the low-temperature end of the intermediate connecting rod. There are also four high-temperature inner ring fixing bracket connecting rods, which are evenly fixed at 90° on the high-temperature end of the intermediate connecting rod.

10. A gas turbine, characterized in that, It includes a magnetic levitation support system for a thin-walled drum bladed disk rotor as described in any one of claims 1-9.

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